CN108058832B - Combined type anti-icing liquid-air bag anti-icing and deicing system - Google Patents
Combined type anti-icing liquid-air bag anti-icing and deicing system Download PDFInfo
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- CN108058832B CN108058832B CN201711075551.4A CN201711075551A CN108058832B CN 108058832 B CN108058832 B CN 108058832B CN 201711075551 A CN201711075551 A CN 201711075551A CN 108058832 B CN108058832 B CN 108058832B
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- icing
- deicing
- air bag
- leading edge
- airfoil
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/06—Liquid application
- B64D15/08—Liquid application exuded from surface
Abstract
The invention belongs to the field of airplane wing surface deicing, and particularly relates to a composite anti-icing liquid-air bag anti-icing system which comprises a controller (1), an anti-icing liquid tank (2), a pump (3) and an air bag deicing assembly (4), wherein the air bag deicing assembly (4) comprises a deicing air bag (5) and an air flow distribution device (6), the transition positions of an anti-icing liquid spraying area on the upper surface and an anti-icing liquid spraying area on the lower surface of a wing surface leading edge (7) and an air bag deicing area are provided with step-shaped sags, and a plurality of micropores (8) are formed near the wing surface leading edge line and on the side surface of the step-shaped sags. The combined type anti-icing liquid-air bag anti-icing and deicing system improves the deicing efficiency of the airfoil and increases the flight safety margin in the icing environment in a combined type anti-icing and deicing mode.
Description
Technical Field
The invention relates to the field of airplane airfoil deicing, in particular to a composite anti-icing liquid-air bag anti-icing system.
Background
After the airplane enters an icing environment, ice accumulation occurs at the leading edge of the airplane airfoil, and the flight safety is affected. The existing anti-icing and deicing methods comprise an anti-icing liquid anti-icing system, an air bag anti-icing system and the like. The anti-icing system of the anti-icing liquid can not influence the aerodynamic performance of the wing surface, the energy consumption on the airplane is less, but the loading capacity of the anti-icing liquid is limited, so that the anti-icing time is limited (particularly, the anti-icing time is limited when the anti-icing area is large), and the effective load of the airplane is reduced by loading the anti-icing liquid; the air bag deicing system is simple in structure, small in system weight and low in energy consumption on the machine, and the airfoil surface is easy to produce residual ice after deicing to influence the aerodynamic performance of the airfoil surface. Due to the fact that the anti-icing liquid anti-icing system and the air bag anti-icing system are different in structure and the anti-icing control time sequence is different, the combined type anti-icing liquid-air bag anti-icing system is difficult to develop and is not applied to an active airplane.
Disclosure of Invention
The invention aims to design a composite anti-icing liquid-air bag anti-icing system based on the existing anti-icing and deicing technology of an airplane by combining the anti-icing liquid anti-icing technology and the air bag anti-icing technology. So as to improve the deicing efficiency and increase the flight safety margin.
In view of the above problems of the prior art, according to one aspect of the present disclosure, the following technical solutions are adopted in the present invention:
a composite anti-icing liquid-air bag anti-icing system comprises a controller, an anti-icing liquid tank, a pump and an air bag deicing assembly. The air bag deicing assembly at least comprises a deicing air bag (installed behind the leading edge of the airplane airfoil) and an air flow distribution device (communicated with an air introducing interface of the deicing air bag and used for blowing air or sucking air to the deicing air bag). When the system works, the controller controls the pump to spray the anti-icing liquid from the anti-icing liquid tank to the position near the leading edge line of the airfoil and controls the air bag deicing assembly to deice the leading edge of the airfoil. On one hand, the system sprays the anti-icing liquid near the front edge line of the airfoil, and the anti-icing liquid flows to the rear of the upper surface and the lower surface of the front edge of the airfoil under the action of airflow to form a liquid film for reducing the freezing point of the liquid, so that the freezing point of supercooled water drops at the front edge of the airfoil is reduced, and the icing difficulty is increased; on the other hand, after ice accretion forms at the leading edge of the airfoil, the sprayed anti-icing liquid will quickly penetrate to the bottom of the ice layer, reducing the bond strength between the ice layer and the aircraft surface. The air bag is combined with the expansion-contraction work of the air bag, the accumulated ice at the leading edge of the residual airfoil is separated and shattered, and the ice is removed under the action of air flow. At the transition position of the anti-icing liquid spraying area and the air sac deicing area, the invention adopts an inclined surface treatment mode to ensure that the transition area can not generate ice accumulation. In the aspect of control time sequence, according to different anti-icing ranges of the airfoils, a known proper control time sequence is selected, so that the coverage range of spraying the anti-icing liquid is not influenced by the operation of the air bag, and the transition area can be completely covered by the anti-icing liquid.
Has the advantages that:
compared with the similar anti-icing liquid anti-icing system, the composite anti-icing liquid-air bag anti-icing system has light weight and smaller aerodynamic performance on wing surfaces than the similar air bag anti-icing system. The combined type anti-icing liquid-air bag anti-icing system ensures that no icing is formed near the front edge line of the airfoil, the accumulated ice behind the front edge of the airfoil is influenced by the anti-icing liquid, the ice accumulation bonding strength is reduced, the air bag deicing efficiency is greatly improved, the airfoil anti-icing efficiency is integrally improved, and the flight safety margin in the icing environment is increased.
Drawings
Fig. 1 is a schematic structural diagram of a composite anti-icing liquid-air bag anti-icing and deicing system provided by the invention.
FIG. 2 is a view of the leading edge of an airfoil.
In FIG. 1, 1 is a controller, 2 is an anti-icing fluid tank, 3 is a pump, 4 is an air bag de-icing assembly (including 5 de-icing air bags and 6 air flow distribution devices), and 7 is a specially treated airfoil leading edge structure.
In FIG. 2, 5 deicing pockets, 8 are specifically treated micropores in the airfoil leading edge structure.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Referring to fig. 1-2, a composite anti-icing fluid-bladder anti-icing system structure and an aircraft airfoil leading edge are illustrated according to embodiments of the present invention.
The embodiment of the invention provides a composite anti-icing liquid-air bag anti-icing system which comprises a controller 1, an anti-icing liquid box 2, a pump machine 3 and an air bag deicing component 4 (a deicing air bag 5 and an air flow distribution device 6). The method comprises the following specific steps:
the controller 1 is respectively connected with the pump machine 3 and the airflow distribution device 6 and sends ice prevention and removal signals to the pump machine 3 and the airflow distribution device 6; the controller 1 is also used to monitor the system operating state.
The anti-icing fluid tank 2 and the pump 3 are arranged in the vicinity of the leading edge 7 of the aircraft airfoil, it being possible to use known anti-icing fluid tanks of suitable volume and pumps of suitable power, the anti-icing fluid tank 2 and the pump 3 communicating for the controlled spraying of the specially treated leading edge 7 of the airfoil with anti-icing fluid.
The air bag deicing assembly 4 is arranged on the outer surface of a specially treated airfoil leading edge 7 and comprises a deicing air bag 5 and an air flow distribution device 6 for controlled air bag inflation deicing of the aircraft airfoil leading edge 7.
A plurality of micropores 8 are formed near the airfoil leading edge line of the aircraft airfoil leading edge 7 and used for spraying anti-icing liquid to the airfoil leading edge 7.
At the transition position of the anti-icing liquid spraying area and the air sac deicing area, the invention adopts a slope processing mode, the upper surface and the lower surface of the wing surface leading edge 7 are both provided with step-shaped depressions, and the side surfaces of the step-shaped depressions are provided with a plurality of micropores 8, so that the ice accumulation in the transition area is avoided.
In specific implementation, when the controller 1 receives an opening signal, a working signal is sent to the pump 3, and the pump 3 extracts the anti-icing liquid from the anti-icing liquid tank 2 and sprays the anti-icing liquid on the outer surface of the specially processed airfoil leading edge 7; meanwhile, the controller 1 sends a working signal to the airflow distribution device 6, on one hand, the system sprays the anti-icing liquid near the micropores 8 of the airfoil leading edge 7, and under the action of the airflow, the anti-icing liquid flows to the rear of the upper surface and the lower surface of the airfoil leading edge 7 to form a liquid film for reducing the liquid freezing point, so that the freezing point of supercooled water drops at the airfoil leading edge 7 is reduced, and the icing difficulty is increased; on the other hand, after ice accretion has formed at the airfoil leading edge 7, the sprayed anti-icing liquid will quickly penetrate to the bottom of the ice layer, reducing the bond strength between the ice layer and the aircraft surface. The air bag is combined with the expansion-contraction work of the air bag, the accumulated ice at the leading edge of the residual airfoil is separated and shattered, and the ice is removed under the action of air flow. The controller 1 is internally preset with a known proper anti-icing and deicing working time sequence, and the composite anti-icing liquid-air bag anti-icing and deicing system works according to the preset time sequence until the controller 1 receives a closing signal.
Claims (3)
1. A combined anti-icing liquid-air bag anti-icing system is characterized by comprising:
The controller (1) is used for receiving an opening/closing signal given by a system switch, sending the signal to the pump (3) and the airbag deicing assembly (4) after the opening signal is obtained, and enabling the pump (3) and the airbag deicing assembly (4) to work according to a preset time sequence;
an anti-icing fluid tank (2) for storing anti-icing fluid;
the pump (3) is used for pumping the anti-icing fluid in the anti-icing fluid box (2) and spraying the anti-icing fluid to the outer surface near the leading edge point of the airfoil leading edge (7);
an air bag de-icing assembly (4) for de-icing the rear side of the leading edge (7) of the aircraft airfoil;
the transition parts of the airfoil leading edge (7), the anti-icing liquid spraying areas on the upper surface and the lower surface of the airfoil leading edge (7) and the air bag deicing areas are provided with step-shaped depressions;
the pump (3) is arranged near the airfoil leading edge (7) and is structurally connected with the airfoil leading edge (7) through a pipeline, and in order to ensure that anti-icing liquid flows into the outer surface of the airfoil leading edge (7) from the inner side of the airfoil leading edge (7), a plurality of micropores (8) are formed near the leading edge line of the airfoil leading edge (7) and used for spraying the anti-icing liquid;
the stepped undercut flank of the airfoil leading edge (7) also has a plurality of micropores (8).
2. A combined ice protection liquid-air bag deicing system according to claim 1, characterized in that the air bag deicing assembly (4) comprises a deicing air bag (5) and an air flow distribution device (6), the deicing air bag (5) is disposed behind a plurality of micropores (8) on the outer surface of the leading edge (7) of the aircraft airfoil, the air flow distribution device (6) receives control commands sent by the controller (1) and is communicated with an air-introducing interface of the deicing air bag (5), air is blown or extracted towards the deicing air bag (5), the ice layer is broken by blowing, and the deicing air bag (5) is restored and reset by extracting air.
3. The system according to claim 1, wherein the controller (1) is preset with a known and suitable deicing operation timing sequence, and the system operates according to the preset timing sequence until the controller (1) receives a closing signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711075551.4A CN108058832B (en) | 2017-11-03 | 2017-11-03 | Combined type anti-icing liquid-air bag anti-icing and deicing system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711075551.4A CN108058832B (en) | 2017-11-03 | 2017-11-03 | Combined type anti-icing liquid-air bag anti-icing and deicing system |
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| CN108058832A CN108058832A (en) | 2018-05-22 |
| CN108058832B true CN108058832B (en) | 2022-06-28 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109720582B (en) * | 2018-11-12 | 2023-06-30 | 中航通飞华南飞机工业有限公司 | Composite electric heating-anti-icing liquid ice prevention and removal system |
| CN109878740B (en) * | 2019-03-25 | 2024-02-27 | 上海工程技术大学 | Anti-icing and deicing device and method for wings and tail wings of turboprop aircraft |
| CN112193420A (en) * | 2020-08-31 | 2021-01-08 | 中电科芜湖通用航空产业技术研究院有限公司 | Micropore seepage liquid structure, aircraft anti-icing system and aircraft |
| CN112977835B (en) * | 2021-05-11 | 2021-08-03 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-overflow device |
| CN113148182A (en) * | 2021-05-31 | 2021-07-23 | 中航(成都)无人机系统股份有限公司 | Unmanned aerial vehicle and wing defroster thereof |
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| CN108058832A (en) | 2018-05-22 |
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